EP0396736A1 - Sustainer propulsion system - Google Patents
Sustainer propulsion systemInfo
- Publication number
- EP0396736A1 EP0396736A1 EP90901131A EP90901131A EP0396736A1 EP 0396736 A1 EP0396736 A1 EP 0396736A1 EP 90901131 A EP90901131 A EP 90901131A EP 90901131 A EP90901131 A EP 90901131A EP 0396736 A1 EP0396736 A1 EP 0396736A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- engine
- casing
- propulsion system
- missile
- outlet
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- This invention relates to a propulsion system for a missile, and more specifically, to the particular arrange- ment of components therein.
- propulsion systems for small- sub ⁇ sonic missiles have been limited to solid rocket engines at thrust levels under 100 lbs.
- the solid rocket engine has the attraction of being simple and low in cost, but has the disadvantages of high fuel consumption and lack of control ⁇ lability.
- a small turbojet offers low fuel consumption and throttle control for hover, cruise and dash modes but has not found wide application due to its complexity and high manufacturing cost when compared to the solid propellant motor.
- the present invention is directed to overcoming one or more of the above problems associated with a propul ⁇ sion system including a turbojet engine.
- An exemplary embodiment of the invention achieves the foregoing object in a propulsion system for a missile comprising a gas turbine engine including a housing mounted to a flange within a circular casing of the missile.
- the engine includes an air inlet to a compressor and an exhaust gas outlet.
- the system includes inlet means located forward of the engine for directing free stream air through the missile casing and into the compressor inlet, outlet means aft of the engine for directing engine exhaust gas through the missile casing and into free stream air, engine start means mounted aft of the engine outlet, fuel storing means mounted forward of the engine within the inlet means, fuel delivery means associated with the storing means for deliv ⁇ ering fuel to the engine, and means for controlling and sequencing the engine.
- the inlet means comprises two curved ducts with forward facing scoops where the ducts direct free stream air through openings in the missile casing and into the compressor inlet of the engine.
- the ducts are attached to the circular casing such that the ducts are diametrically opposite to each other.
- the two ducts are coupled directly to the compressor inlet.
- the propulsion system includes a plenum within the casing and forward of the compressor inlet.
- the two ducts terminate in the plenum, and the free stream air directed through the two ducts is dumped to the plenum ahead of the compressor inlet.
- the outlet means comprises a bifurcated duct coupled to the engine outlet, which passes through openings in the missile casing and terminates in two rearward facing nozzles.
- the outlet means comprises a single duct, coupled to the engine outlet, which passes through an opening in the missile casing and terminates in a single rearward facing nozzle above the casing.
- the engine start means comprises an insulated start cartridge mounted on a bracket supported by the missile casing aft of the engine outlet, and an ignitor mounted on the aft end of the engine housing.
- the fuel storing means comprises a bladder tank mounted within the inlet means to a flange in the missile casing.
- the fuel delivery means comprises a pressurization bottle mounted to the missile casing, a fuel pressure regulator, a pyrotechnically operated valve for directing fuel flow and providing zero leakage during storage, and a torque motor operated single- stage servo valve mounted on a missile casing supported bracket aft of the outlet means for scheduling engine fuel flow as a function of a signal from the control means.
- FIG. 1 is a somewhat schematic, horizontal section of an exemplary embodiment of a propulsion system according to the invention
- Fig. 2 is a vertical section of the inlet configu ⁇ ration of the exemplary embodiment of the invention taken approximately along line 2-2 of Fig. 1;
- Fig. 3 is a vertical section of the outlet config ⁇ uration of the exemplary embodiment of the invention taken approximately along line 3-3 of Fig. 1;
- Fig. 4 is a somewhat schematic, horizontal section of an alternate embodiment of a propulsion system
- Fig. 5 is a vertical section of the inlet configu ⁇ ration of the alternate taken approximately along line 5-5 of Fig. 4;
- Fig. 6 is a somewhat schematic, vertical section of an alternate embodiment of the outlet of the propulsion system of the invention;
- Fig. 7 is a rear elevation of the alternate embodiment of the outlet of the propulsion system of the invention.
- Fig. 8 is a schematic of the fuel delivery system of the propulsion system of the invention.
- FIG. 1 An exemplary embodiment of a propulsion system according to the invention, generally designated 12, is illustrated in Fig. 1.
- the propulsion system 12 is located in a cylindrical missile hull or casing 14 having a flange 16 to which is mounted an engine 18, more specifically, a turbojet engine.
- the engine 18 forms no part of the present invention but may be in the form of that disclosed in the commonly assigned copending application of Shekleton et al.. Serial No. 065,258, filed June 22, 1987, the details of which are herein incorporated by reference.
- the engine 18 includes an inlet 20 to a compressor 22 and an exhaust gas outlet 24.
- the propulsion system 12 includes inlet means located forward of the compressor inlet 20 for directing free stream air, generally designated A, through the circular casing 14 and into the compressor inlet 20.
- the inlet means is comprised of two diametrically opposite curved ducts 26 attached to the casing 14, and directly coupled to the inlet 20 of the compressor 22.
- the ducts 26 are composed of fiberglass rein ⁇ forced plastic to minimize weight.
- the ducts 26 include forward facing scoops 28 which direct free stream air A through openings 29 in the casing 14 and directly into the inlet 20 of the compressor 22. In operation, the forward facing scoops 28 will be sized for optimum recovery of free stream air at a missile flight speed of approximately 150 m/s. As shown in Figs.
- the exemplary embodi ⁇ ment of the propulsion system 12 further includes outlet means comprised of a bifurcated duct 30 passing through openings 31 in the casing 14.
- the bifurcated duct 30 is attached to and is completely supported at the rear of the engine 18.
- the openings 31 through which the duct 30 passes are appropriately sized to avoid contact between the duct 30 and the casing 14. Cooling air at ram pressure is admitted through holes in the engine mounting flange 16, then flows through the interior of the casing 14 and a compartment around the duct 30 to discharge through a space 32 between the duct 30 and the casing 14.
- the bifurcated duct 30 terminates in two diamet ⁇ rically opposite rearward facing nozzles 33 which are typically inclined at an angle of approximately 10 degrees to the missile center line 34 to prevent direct impingement of hot exhaust gases onto the downstream body.
- the inclina ⁇ tion will result in a actual thrust loss of only approxi ⁇ mately 2%.
- the inlet means includes a plenum 36 within the casing 14 forward of the inlet 20 of the compressor 22 and opposed ducts 37.
- the two ducts 37 are not coupled directly to the compressor inlet 20 but, rather, terminate in the plenum 36 so that the free stream air A directed through the forward facing scoops 28 and the two ducts 37 is dumped to the plenum 36 ahead of the inlet 20 to the compressor 22.
- the outlet means may comprise a single duct 38 coupled to the engine outlet 24, rather than the bifurcated duct 30.
- the duct 38 passes through an opening 39 in the missile casing 14 and terminates in a rearward facing nozzle 40 located above the casing 14 so that the heat of exhaust gases is screened by the missile from ground based observers.
- the propulsion system 12 further includes engine start means, fuel storing means, and fuel delivery means.
- engine start means for the purpose of further describing these components, reference is made solely to the exemplary embodiment of Fig. 1 since these components are identical and similarly situated notwithstanding the particular configuration of the inlet and outlet means.
- the propulsion system 12 includes engine start means comprising a conventional start cartridge 42 centrally mounted on a casing supported bracket (not shown) aft of the engine outlet 24.
- the start car ⁇ tridge 42 is adequately insulated to maintain adjacent component and structure temperatures at required levels. Compartment cooling air flow removes heat during flight.
- the engine start means further comprises a conventional ignitor 44, which is mounted on the aft end of the engine housing, and causes the initial ignition of fuel during engine start.
- the propulsion system includes engine start means comprising a conventional start cartridge 42 centrally mounted on a casing supported bracket (not shown) aft of the engine outlet 24.
- the start car ⁇ tridge 42 is adequately insulated to maintain adjacent component and structure temperatures at required levels. Compartment cooling air flow removes heat during flight.
- the engine start means further comprises a conventional ignitor 44, which is mounted on the aft end of the engine housing, and causes the initial ignition of fuel during engine start.
- the propulsion system is shown in Fig
- fuel storing means comprising a bladder tank 46 mounted in the forward end of the casing 14 between the inlet ducts 26.
- the propulsion system 12 depicted in Fig. 1 includes fuel delivery means.
- the fuel delivery means is comprised of basing or engine mounted gas bottle 48 from which fuel pressure is derived.
- the gas bottle 48 is pressurized with nitrogen and is manufactured from aluminum with fiberglass filament winding to provide high strength and light weight.
- the fuel delivery means additionally comprises a fuel pressure regulator 50, and a pyrotechnically operated valve assembly 52 for directing fuel flow and providing zero leakage during storage.
- the pressure regulator 50 and the pyrotechnically operated valve 52 are both located in the forward end of the casing 14 between the inlet ducts 26 adjacent the bladder fuel tank 46.
- the pyrotechnically operated valve 52 is constructed of stain ⁇ less steel and operates in a manner such that it causes a ram (not shown) to rupture an integral metal diaphragm (not shown) to permit the flow of fuel from the bladder fuel tank 46.
- the fuel delivery means comprises a fuel servo valve 54, located within the casing 14 aft of the engine outlet 24 and adjacent the start cartridge 42, which is conventionally used to schedule engine fuel flow as a function of a signal from a conventional control means (not shown) .
- the fuel servo valve 54 is a single-stage, torque motor operated, flapper type valve and is insulated and/or shielded to maintain an acceptable temperature.
- the fuel delivery means of the present invention provides for long term storage and rapid fuel system pres ⁇ surization in any orientation. All components are self-con ⁇ tained to provide maximum reliability throughout all envi ⁇ ronmental conditions. From the foregoing, it will be appreciated that the invention provides a propulsion system, incorporating a turbojet engine, wherein the various components are arranged to provide a compact, efficient propulsion system.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
On peut réduire les coûts de fabrication inhérents aux systèmes de propulsion à turboréacteur (12) pour un engin ayant un moteur (18) monté dans un logement (14), muni d'un canal d'admission (20) à un compresseur (22) et d'un canal de sortie des gaz d'échappement (24), grâce à une structure qui se compose d'un groupe de propulsion (12) pourvu d'un canal d'admission (26, 28) situé à l'avant du moteur (18) et qui permet de diriger vers le canal d'admission (20) du compresseur (22) un flux d'air libre, d'un canal de sortie (30, 33) situé à l'arrière du moteur (18) qui permet de diriger le gaz d'échappement dans le flux d'air libre, d'un démarreur de moteur (42) à l'arrière du canal de sortie du moteur (24), et d'une réserve de carburant (46) monté à l'avant du moteur (18).The manufacturing costs inherent in turbojet propulsion systems (12) can be reduced for a machine having an engine (18) mounted in a housing (14), provided with an intake channel (20) to a compressor (22 ) and an exhaust gas outlet channel (24), thanks to a structure which consists of a propulsion unit (12) provided with an intake channel (26, 28) located at the front of the engine (18) and which makes it possible to direct towards the intake channel (20) of the compressor (22) a flow of free air, from an outlet channel (30, 33) located at the rear of the engine (18) which directs the exhaust gas into the free air flow, an engine starter (42) at the rear of the engine outlet channel (24), and a fuel reserve (46) mounted at the front of the engine (18).
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US263397 | 1988-10-27 | ||
US07/263,397 US4938021A (en) | 1988-10-27 | 1988-10-27 | Sustainer propulsion system |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0396736A1 true EP0396736A1 (en) | 1990-11-14 |
EP0396736A4 EP0396736A4 (en) | 1991-04-03 |
Family
ID=23001618
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19900901131 Withdrawn EP0396736A4 (en) | 1988-10-27 | 1989-09-29 | Sustainer propulsion system |
Country Status (4)
Country | Link |
---|---|
US (1) | US4938021A (en) |
EP (1) | EP0396736A4 (en) |
JP (1) | JP2818288B2 (en) |
WO (1) | WO1990004714A1 (en) |
Families Citing this family (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4887425A (en) * | 1988-03-18 | 1989-12-19 | General Electric Company | Fuel spraybar |
US5150569A (en) * | 1990-12-14 | 1992-09-29 | Williams International Corporation | Integrated propulsion system |
US5161369A (en) * | 1991-01-28 | 1992-11-10 | Williams International Corporation | Aft fan gas turbine engine |
US5483791A (en) * | 1994-06-14 | 1996-01-16 | Alliedsignal Inc. | Turboprop with impeller inlet strake |
US6209309B1 (en) | 1997-12-19 | 2001-04-03 | Hamilton Sundstrand Corporation | Pulse width modulated fuel flow control for an engine |
AU2001260966A1 (en) | 2000-01-12 | 2001-08-07 | Allison Advanced Development Company | Propulsion module |
US7407133B2 (en) * | 2001-07-24 | 2008-08-05 | 3X Jet Aircraft Company | Using imbalanced thrust in a multi-engine jet aircraft |
DE10215551A1 (en) * | 2002-04-09 | 2003-10-23 | Rolls Royce Deutschland | Turboprop aircraft engine |
US6941760B1 (en) * | 2003-03-19 | 2005-09-13 | Hamilton Sundstrand Corporation | Start system for expendable gas turbine engine |
US8360356B2 (en) * | 2008-07-17 | 2013-01-29 | W. Eric Moore | Flying apparatus |
US8714919B2 (en) * | 2009-11-06 | 2014-05-06 | Raytheon Company | Inlet and exhaust system |
US9234460B2 (en) * | 2012-05-22 | 2016-01-12 | Sikorsky Aircraft Corporation | Engine inlet |
US9194330B2 (en) * | 2012-07-31 | 2015-11-24 | United Technologies Corporation | Retrofitable auxiliary inlet scoop |
US10260427B2 (en) | 2013-03-15 | 2019-04-16 | United Technologies Corporation | Variable area bypass nozzle |
WO2014165364A1 (en) | 2013-04-02 | 2014-10-09 | United Technologies Corporation | Bifurcated air inlet housing for a gas turbine engine |
CN103587520B (en) * | 2013-11-25 | 2016-08-17 | 中国南方航空工业(集团)有限公司 | The jet pipe of hovercar |
US11041442B2 (en) | 2017-12-06 | 2021-06-22 | Williams International Co., L.L.C. | Self-eroding single-use gas-turbine-engine igniter |
CN111216901A (en) | 2018-11-26 | 2020-06-02 | 本田技研工业株式会社 | Power supply device and flying object |
US20210070461A1 (en) * | 2019-09-08 | 2021-03-11 | Bell Textron Inc. | Aircraft with bifurcated air inlet |
Citations (8)
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---|---|---|---|---|
US2621719A (en) * | 1947-05-03 | 1952-12-16 | Curtiss Wright Corp | Constant center-of-gravity liquid supply system |
US2808700A (en) * | 1953-12-11 | 1957-10-08 | Kretschmer Willi | Propellant supply systems for jet reaction motors |
US3025667A (en) * | 1957-07-22 | 1962-03-20 | Boeing Co | Rotary turret reversible thrust noise suppression jet engine nozzles |
US3486339A (en) * | 1967-10-26 | 1969-12-30 | Thiokol Chemical Corp | Gas generator nozzle for ducted rockets |
GB2044359A (en) * | 1979-03-16 | 1980-10-15 | Rolls Royce | Gas turbine engine air intakes |
EP0103384A2 (en) * | 1982-08-17 | 1984-03-21 | The De Havilland Aircraft Of Canada, Limited | Air intake system for engine |
GB2148809A (en) * | 1978-03-14 | 1985-06-05 | Rolls Royce | Self-propelled missile |
US4762293A (en) * | 1967-12-13 | 1988-08-09 | The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kindgom Of Great Britain And Northern Ireland | Rocket projectiles |
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NL63500C (en) * | 1945-02-01 | |||
US2977753A (en) * | 1954-02-13 | 1961-04-04 | Rech Etudes Prod | Improvements in continuous flow gas engines |
US3112903A (en) * | 1955-05-31 | 1963-12-03 | Earl W Conrad | Combination fuel tank and ram jet power plant |
US2936973A (en) * | 1957-09-06 | 1960-05-17 | Gen Electric | Vtol aircraft |
US3143852A (en) * | 1961-09-08 | 1964-08-11 | John M Alderson | Ram jet engine |
US3313500A (en) * | 1965-04-30 | 1967-04-11 | Lockheed Aircraft Corp | Flight control means for aircraft |
US3703998A (en) * | 1970-12-28 | 1972-11-28 | Teledyne Ryan Aeronautical Co | Drone aircraft with telescopic fuselage |
US4674286A (en) * | 1972-09-29 | 1987-06-23 | Arthur K. Thatcher | Sonic dispersion unit and control system therefor |
US3843277A (en) * | 1973-02-14 | 1974-10-22 | Gen Electric | Sound attenuating inlet duct |
US3917117A (en) * | 1973-05-21 | 1975-11-04 | Sundstrand Corp | Positive expulsion fuel tank, and bladder dispenser therefor |
US3834161A (en) * | 1973-06-01 | 1974-09-10 | Us Air Force | Dual mode auxiliary power unit |
US3998050A (en) * | 1974-01-07 | 1976-12-21 | The United States Of America As Represented By The Secretary Of The Air Force | Reverse flow aft inlet ramjet system |
US4192336A (en) * | 1975-12-29 | 1980-03-11 | The Boeing Company | Noise suppression refracting inlet for jet engines |
US4096803A (en) * | 1976-12-27 | 1978-06-27 | The United States Of America As Represented By The Secretary Of The Army | Solid propellant air turbo rocket |
US4434621A (en) * | 1981-09-04 | 1984-03-06 | Teledyne Industries, Inc. | Engine fuel system |
US4570658A (en) * | 1983-08-15 | 1986-02-18 | The United States Of America As Represented By The Secretary Of The Navy | Pyrotechnic-actuated dual air valve |
FR2561743B1 (en) * | 1984-03-21 | 1986-09-05 | Aerospatiale | PYROTECHNIC VALVE |
JPS62140629A (en) * | 1985-12-12 | 1987-06-24 | Mitsubishi Heavy Ind Ltd | Method for removing mercury contained in combustion exhaust gas |
JPS62140628A (en) * | 1985-12-12 | 1987-06-24 | Mitsubishi Heavy Ind Ltd | Method for removing mercury contained in combustion exhaust gas |
JPS62140627A (en) * | 1985-12-12 | 1987-06-24 | Mitsubishi Heavy Ind Ltd | Method for removing mercury contained in combustion exhaust gas |
JPS62186925A (en) * | 1986-02-13 | 1987-08-15 | Mitsubishi Heavy Ind Ltd | Treatment of exhaust gas |
-
1988
- 1988-10-27 US US07/263,397 patent/US4938021A/en not_active Expired - Fee Related
-
1989
- 1989-09-29 EP EP19900901131 patent/EP0396736A4/en not_active Withdrawn
- 1989-09-29 JP JP2501173A patent/JP2818288B2/en not_active Expired - Lifetime
- 1989-09-29 WO PCT/US1989/004293 patent/WO1990004714A1/en not_active Application Discontinuation
Patent Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2621719A (en) * | 1947-05-03 | 1952-12-16 | Curtiss Wright Corp | Constant center-of-gravity liquid supply system |
US2808700A (en) * | 1953-12-11 | 1957-10-08 | Kretschmer Willi | Propellant supply systems for jet reaction motors |
US3025667A (en) * | 1957-07-22 | 1962-03-20 | Boeing Co | Rotary turret reversible thrust noise suppression jet engine nozzles |
US3486339A (en) * | 1967-10-26 | 1969-12-30 | Thiokol Chemical Corp | Gas generator nozzle for ducted rockets |
US4762293A (en) * | 1967-12-13 | 1988-08-09 | The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kindgom Of Great Britain And Northern Ireland | Rocket projectiles |
GB2148809A (en) * | 1978-03-14 | 1985-06-05 | Rolls Royce | Self-propelled missile |
GB2044359A (en) * | 1979-03-16 | 1980-10-15 | Rolls Royce | Gas turbine engine air intakes |
EP0103384A2 (en) * | 1982-08-17 | 1984-03-21 | The De Havilland Aircraft Of Canada, Limited | Air intake system for engine |
Non-Patent Citations (2)
Title |
---|
AVIATION WEEK AND SPACE TECHNOLOGY. vol. 121, no. 13, 24 September 1984, NEW YORK US page 66 ""Boeing Develops Multipurpose,Inexpensive Drone for Military"" * |
See also references of WO9004714A1 * |
Also Published As
Publication number | Publication date |
---|---|
JPH03502125A (en) | 1991-05-16 |
JP2818288B2 (en) | 1998-10-30 |
US4938021A (en) | 1990-07-03 |
EP0396736A4 (en) | 1991-04-03 |
WO1990004714A1 (en) | 1990-05-03 |
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Free format text: STATUS: THE APPLICATION HAS BEEN WITHDRAWN |
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18W | Application withdrawn |
Withdrawal date: 19910731 |